Drive system for translating structure

ABSTRACT

A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

FIELD

The present disclosure relates generally to nacelle systems and, moreparticularly, to translating components of nacelle systems and drivesystems used to translate such components.

BACKGROUND

Modern aircraft typically utilize one or more gas turbine engines forpropulsion. The engines may be housed in a nacelle, which may bewing-mounted, fuselage-mounted, tail-mounted, or some combinationthereof. Typical turbofan jet engines include a fan that draws anddirects a flow of ambient air into the nacelle and into and around anengine core to form, respectively, a core engine flow and a bypass flow.The core engine flow is initially passed through a compressor and thenthrough a combustor where a pressurized core engine flow is mixed withfuel and ignited. Combustion of the fuel and air mixture results in astream of high temperature and high pressure gas that is used to rotatea turbine downstream of the combustor. The compressor and the fan arerotated via connection to the rotating turbine. The gas exiting theturbine is thereafter directed through an exhaust nozzle at the rear ofthe engine and expelled to the atmosphere.

The bypass flow is directed about the engine core and constrained by aninner wall of the nacelle. In turbofan engines, the bypass flowtypically provides the main thrust for an aircraft. The bypass flow mayalso be used to decelerate an aircraft after landing or during arejected takeoff. Thrust reversers mounted in the structure of thenacelle selectively reverse the direction of the bypass flow via acascade array to generate reverse thrust. One or more blocker doors maybe situated on the translating sleeve and deployed into the bypass flow.Once deployed, the blocker doors redirect a portion of the bypass flowinto and through the cascade array to produce a flow of high-velocityair having a vector component in the forward direction, reversing thethrust of the engine and thereby decelerating the aircraft.

During normal engine operation, the bypass flow exits the engine througha fan nozzle, typically disposed radially outward of the exhaust nozzle.Some aircraft nacelles have a variable area fan nozzle (VAFN) configuredto slide, pivot, or otherwise open to increase or decrease the area ofone or more aft opening(s) through which the bypass flow may exit thenacelle. By selectively varying the exit area of the fan nozzle, variousoperating characteristics—e.g., the fan pressure ratio of the engine—maybe adjusted to match a particular flight condition. VAFN structures aretypically disposed aft of and connected to one or more translatingsleeves of the thrust reverser.

SUMMARY

A drive system for deploying blocker doors on a translating nozzle of avariable area fan nozzle of a nacelle relative to a thrust reverser anda fixed structure of the nacelle is disclosed herein. In accordance withvarious embodiments, the drive system may comprise a primary actuator, atorque shaft, and a secondary actuator operationally coupled to theprimary actuator via the torque shaft. The primary actuator may includean opening actuator configured to attach to the fixed structure, aclosing actuator configured to attach to the fixed structure, a firstprimary rod configured to be driven by the opening actuator, a secondprimary rod configured to be driven by the closing actuator, and aprimary gear rotationally coupled to the first primary rod and thesecond primary rod. The torque shaft may be rotationally coupled to theprimary gear. The secondary actuator may comprise a secondary gearrotationally coupled to the torque shaft and a secondary rod configuredto be driven linearly by the secondary gear.

In various embodiments, the secondary rod may include a plurality ofteeth configured to engage the secondary gear. In various embodiments,the secondary rod may be configured to attach to the translating nozzle.In various embodiments, the primary gear may be configured to attach tothe thrust reverser.

In various embodiments, the drive system may further comprise a lockingassembly configured to restrict translation of the translating nozzlerelative to the thrust reverser in response to deployment of the thrustreverser. In various embodiments, the locking assembly may comprise aninterference member biased toward the primary gear, and a contact membercoupled to the interference member and configured to contact the fixedstructure when the thrust reverser is in a stowed configuration.

A drive system for translating a translating sleeve of a thrust reverserof a nacelle relative to a fixed structure of the nacelle is alsodisclosed herein. In accordance with various embodiments, the drivesystem may comprise a first primary actuator, a torque shaft, and asecondary actuator operationally coupled to the first primary actuatorvia the torque shaft. The first primary actuator may include a firstprimary rod configured to attach to the fixed structure, and a firstprimary gear rotationally coupled to the first primary rod. The torqueshaft may be rotationally coupled to the first primary gear. Thesecondary actuator may be configured to translate a blocker door of thethrust reverser between a stowed-blocker-door position and adeployed-blocker-door position in response to rotation of the firstprimary gear.

In various embodiments, the secondary actuator may comprise a secondarygear rotationally coupled to the torque shaft, and a secondary rodincluding a plurality of teeth configured to engage the secondary gear.The secondary rod may be configured to translate the blocker door inresponse to rotation of the secondary gear.

In various embodiments, the secondary actuator may comprise a secondarygear system rotationally coupled to the torque shaft, and a link coupledto the secondary gear system. The link may be configured to translatethe blocker door in response to rotation of the secondary gear system.

In various embodiments, the first primary gear may be configured totranslate linearly relative to the first primary rod in response to adeployment of the translating sleeve.

In various embodiments, the secondary actuator may be configured totranslate the blocker door to the deployed-blocker-door position inresponse to rotation of the first primary gear in a firstcircumferential primary gear direction. In various embodiments, thesecondary actuator may be configured to translate the blocker door tothe stowed-blocker-door position in response to rotation of the firstprimary gear in a second circumferential primary gear direction oppositethe first circumferential primary gear direction.

In various embodiments, the drive system may further comprise a secondprimary actuator including a second primary rod configured to attach tothe fixed structure and a second primary gear rotationally coupled tothe second primary rod.

A nacelle is also disclosed herein. In accordance with variousembodiments, the nacelle may comprise a fixed structure, a firsttranslating structure configured to translate relative to the fixedstructure, and a first drive system operationally coupled to the firsttranslating structure. The first drive system may comprise a firstprimary actuator, a first torque shaft, and a first secondary actuatoroperationally coupled to the first primary actuator via the first torqueshaft. The first primary actuator may be coupled to the fixed structureand may include a first primary rod and a first primary gearrotationally coupled to the first primary rod. The first torque shaftmay be rotationally coupled to the first primary gear.

In various embodiments, the nacelle may further comprise a thrustreverser including a translating sleeve and a blocker door. The firsttranslating structure may comprise the translating sleeve of the thrustreverser. The first secondary actuator may be configured to translatethe blocker door of the thrust reverser between a stowed-blocker-doorposition and a deployed-blocker-door position in response to rotation ofthe first primary gear.

In various embodiments, the nacelle may further comprise a variable areafan nozzle including a translating nozzle. The first translatingstructure may comprise the translating nozzle. The first secondaryactuator may comprise a secondary gear rotationally coupled to the firsttorque shaft, and a secondary rod coupled to the translating nozzle andconfigured to be driven linearly by the secondary gear.

In various embodiments, the nacelle may further comprise a secondtranslating structure configured to translate relative to the fixedstructure and the first translating structure. A second drive system maybe operationally coupled to the second translating structure. The seconddrive system may comprise a second primary actuator coupled to the fixedstructure and including a second primary rod and a second primary gearrotationally coupled to the second primary rod, a second torque shaftrotationally coupled to the second primary gear, and a second secondaryactuator operationally coupled to the second primary actuator via thesecond torque shaft.

In various embodiments, the nacelle may further comprise a thrustreverser and a variable area fan nozzle including a translating nozzle.The thrust reverser may include a translating sleeve and a blocker door.The variable area fan nozzle may include a translating nozzle. The firsttranslating structure may comprise the translating sleeve of the thrustreverser. The first secondary actuator may be configured to translatethe blocker door of the thrust reverser between a stowed-blocker-doorposition and a deployed-blocker-door position in response to rotation ofthe first primary gear. The second translating structure may comprisethe translating nozzle. The second secondary actuator may comprise asecondary gear rotationally coupled to the second torque shaft, and asecondary rod coupled to the translating nozzle and configured to bedriven linearly by the secondary gear.

In various embodiments, the second drive system may further comprise alocking assembly configured to restrict a translation of the translatingnozzle relative to the translating sleeve in response to a translationof the translating sleeve away from the fixed structure.

In various embodiments, the locking assembly may comprise aninterference member biased toward the second primary gear of the seconddrive system, and a contact member coupled to the interference memberand configured to contact the fixed structure when the thrust reverseris in a stowed configuration.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter of the present disclosure is particularly pointed outand distinctly claimed in the concluding portion of the specification. Amore complete understanding of the present disclosure, however, may bestbe obtained by referring to the following detailed description andclaims in connection with the following drawings. While the drawingsillustrate various embodiments employing the principles describedherein, the drawings do not limit the scope of the claims.

FIG. 1A is a perspective view of an aircraft engine having a translatingcascade-type thrust reverser and a translating variable area fan nozzle,in accordance with various embodiments;

FIG. 1B is a cross sectional view of the aircraft engine illustrated inFIG. 1A, in accordance with various embodiments;

FIG. 1C is a close up cross sectional view of the translatingcascade-type thrust reverser and the translating variable area fannozzle illustrated in FIGS. 1A and 1B, in accordance with variousembodiments;

FIG. 2A is a schematic view of a translating sleeve thrust reverser in astowed configuration and a drive system configured to translate atranslating sleeve of the thrust reverser, in accordance with variousembodiments;

FIG. 2B is a schematic view of a translating sleeve thrust reverser in adeployed configuration and a drive system configured to translate atranslating sleeve of the thrust reverser, in accordance with variousembodiments;

FIG. 3A is a schematic view of a translating sleeve thrust reverser in astowed configuration, a variable area fan nozzle in a closed position,and a drive system configured to translate a translating nozzle of thevariable area fan nozzle and having a lock assembly unlocked state, inaccordance with various embodiments;

FIG. 3B is a schematic view of a translating sleeve thrust reverser in astowed configuration, a variable area fan nozzle in an open position,and a drive system configured to translate a translating nozzle of thevariable area fan nozzle and having a lock assembly in an unlockedstate, in accordance with various embodiments;

FIG. 3C is a schematic view of a translating sleeve thrust reverser in adeployed configuration, a variable area fan nozzle in an open position,and a drive system configured to translate a translating nozzle of thevariable area fan nozzle and having a lock assembly in a locked state,in accordance with various embodiments;

FIG. 4A is a schematic view of a translating sleeve thrust reverser in astowed configuration and a drive system configured to control a positionof the blocker doors of the thrust reverser, in accordance with variousembodiments;

FIG. 4B is a schematic view of a translating sleeve thrust reverser in adeployed configuration and a drive system configured to control aposition of the blocker doors of the thrust reverser, in accordance withvarious embodiments; and

FIG. 5 is a schematic view of a translating sleeve thrust reverser in astowed configuration and a drive system configured to control a positionof the blocker doors of the thrust reverser, in accordance with variousembodiments.

DETAILED DESCRIPTION

The following detailed description of various embodiments herein makesreference to the accompanying drawings, which show various embodimentsby way of illustration. While these various embodiments are described insufficient detail to enable those skilled in the art to practice thedisclosure, it should be understood that other embodiments may berealized and that changes may be made without departing from the scopeof the disclosure. Thus, the detailed description herein is presentedfor purposes of illustration only and not of limitation. Furthermore,any reference to singular includes plural embodiments, and any referenceto more than one component or step may include a singular embodiment orstep. Also, any reference to attached, fixed, connected, or the like mayinclude permanent, removable, temporary, partial, full or any otherpossible attachment option. Additionally, any reference to withoutcontact (or similar phrases) may also include reduced contact or minimalcontact. It should also be understood that unless specifically statedotherwise, references to “a,” “an” or “the” may include one or more thanone and that reference to an item in the singular may also include theitem in the plural. Further, all ranges may include upper and lowervalues and all ranges and ratio limits disclosed herein may be combined.

Referring now to the drawings, FIGS. 1A, 1B and 1C illustrateperspective and cross sectional views of a propulsion system 100.Propulsion system 100 includes an engine 106 and a nacelle 108surrounding engine 106. Engine 106 is at least partially housed withinan inner fixed structure 110. A fan 112 of engine 106 is positionedwithin an upstream portion of nacelle 108 and includes a plurality offan blades 114 that are mounted on a rotor. Fan 112 rotates about anengine centerline C_(L), and draws a flow of air through an inlet 116 ofnacelle 108. A bypass duct 118 is defined between engine 106 and nacelle108. The air flow drawn into the propulsion system 100 via inlet 116 ofnacelle 108 is accelerated by fan 112. A portion of the incoming airflow is directed into and through engine 106 as a core engine flow. Abypass flow enters the upstream end of nacelle 108 and flows around andpast engine 106 and inner fixed structure 110. The bypass flow isaccelerated by the fan 112, then passes through bypass duct 118, whichmay include one or more stators 120, and then exits nacelle 108 throughvariable area fan nozzle 104. At the same time, a high-pressure andhigh-temperature exhaust stream exits engine 106 through an exhaustnozzle 122 located at the aft end of engine 106.

Still referring to FIGS. 1A, 1B and 1C, nacelle 108 includes a thrustreverser 102 of the translating-sleeve-cascade-type and a variable areafan nozzle 104 of the translating-type, in accordance with variousembodiments. In to FIGS. 1A, 1B and 1C, thrust reverser 102 and variablearea fan nozzle 104 are shown in the stowed configuration and the closedposition, respectively. Thrust reverser 102 may be positioned forward ofvariable area fan nozzle 104. More specifically, in various embodiments,thrust reverser 102 includes a translating sleeve 125. Translatingsleeve 125 may include one or more translating sleeve sections, such as,for example, a first translating sleeve section 124 and a secondtranslating sleeve section 126 positioned opposite first translatingsleeve section 124, with both first and second translating sleevesections 124, 126 positioned forward of a translating nozzle 128 ofvariable area fan nozzle 104. Translating sleeve 125 is configured totranslate in the fore and aft directions (as indicated by bidirectionalarrow 130) and is operated by a sleeve actuator 132 (or a plurality ofsleeve actuators spaced circumferentially about engine 106). Translatingsleeve 125, when in the stowed configuration, covers a cascade array 134(or an array of cascade passages). Translation of translating sleeve 125in the aft direction to a deployed configuration results in deploymentof a blocker door 136 (or a plurality of blocker doors spacedcircumferentially about engine 106), as indicated by the directionalarrow 138 in FIG. 1C. Deployment of blocker door(s) 136 into bypass duct118 causes a portion of the bypass flow to exit bypass duct 118 throughcascade array 134, which turns the exiting flow in a generally forwarddirection to create reverse thrust.

Translating nozzle 128 of variable area fan nozzle 104 may beselectively adjusted as engine 106 operates under different flightconditions. As discussed above, such an adjustment may be used to matchengine performance to particular flight conditions. As shown in FIG. 1B,translating nozzle 128 may be selectively translated (e.g., moved foreand aft) to vary an exit area “A_(EXIT)” of the exit of variable areafan nozzle 104 (or a primary fan nozzle exit 142) and to adjust anamount of the bypass flow spilled through an upstream exit 140 formed bya gap between translating nozzle 128 and translating sleeve 125. Forpurposes of illustration, variable area fan nozzle 104 is shown in thecontext of a turbofan jet aircraft engine. Further, in variousembodiments, nacelle 108, having one or both of thrust reverser 102 andvariable area fan nozzle 104, may be mounted to a wing or fuselage of anaircraft, for example, by a pylon or other similar support. In addition,while the disclosure that follows focuses primarily on thrust reverser102 and variable area fan nozzle 104, the disclosure contemplates thesystems and methods described herein to apply to any translatingcomponent, including, for example, and without limitation, translatingnacelle inlet and exit components or surfaces and translating controlsurface components or surfaces, as well as components or surfacesassociated with thrust reversers and variable area fan nozzles.

In various embodiments, translating nozzle 128 is an annularairfoil-like structure mounted proximate the trailing edge oftranslating sleeve 125 and which circumscribes an engine core cowl 144or inner fixed structure 110. Due to the longitudinal variations in thediameter of the engine core cowl 144, selective fore and aft movement oftranslating nozzle 128 changes the size of the exit area A_(EXIT) ofprimary fan nozzle exit 142. As shown in FIG. 1A, translating nozzle 128can include a first nozzle section 127 and a second nozzle section 129,each being generally arcuate in shape and configured to translate in theaxial direction (as indicated by bidirectional arrow 131). Translationof translating nozzle 128 affects a desired size of upstream exit 140,and also varies the outlet geometry and the exit area A_(EXIT) ofprimary fan nozzle exit 142. Hence, when translating nozzle 128 isdeployed, there is an increase in the bypass flow that is dischargedthrough both upstream exit 140 and primary fan nozzle exit 142, which isenlarged as translating nozzle 128 translates in the aft direction. Asillustrated in FIGS. 1A, 1B, and 1C, and as described in further detailbelow, translating nozzle 128 may be selectively translated fore and aftby a drive system 210.

Referring now to FIGS. 2A and 2B, schematic views of thrust reverser 102in a stowed configuration and a deployed configuration, respectively,are provided. In accordance various embodiments, first translatingsleeve section 124 of translating sleeve 125 is translated in fore andaft directions (as indicated by the bidirectional arrow 130) by sleeveactuator 132. Sleeve actuator 132 may comprise any suitable actuationsystem (or main actuator) capable of driving a rapid translation offirst translating sleeve section 124, such as, for example, a ball screwmechanism or a hydraulic cylinder. While FIGS. 2A and 2B illustratefirst translating sleeve section 124, it should be understood thatsecond translating sleeve section 126, with momentary reference to FIG.1A, may include the elements and functionalities as described hereinwith respect to first translating sleeve section 124.

In various embodiments, sleeve actuator 132 is connected between a fixedstructure 152, such as, for example, a torque box, and translatingsleeve 125. In various embodiments, thrust reverser 102 includes blockerdoors 136. As described above, blocker doors 136 are configured to blocka portion of a bypass flow in response to thrust reverser 102translating to a deployed configuration. A primary actuator 160 (or amaster actuator) is connected between fixed structure 152 andtranslating sleeve 125. One or more secondary actuator(s) 162 (or slaveactuators) is/are operationally coupled to primary actuator 160. Eachsecondary actuator is connected to translating sleeve 125 and a blockerdoor 136. While, for clarity, the disclosure generally focuses onoperation of blocker door 136 and secondary actuator 162, it shall beappreciated, as illustrated in FIGS. 2A and 2B, that thrust reverser 102may include a plurality of blocker doors (e.g., a first blocker door136, a second blocker door 136 a, a third blocker door 136 b, and afourth blocker door 136 c) operated by a plurality of secondaryactuators (e.g., a first secondary actuator 162, a second secondaryactuator 162 a, a third secondary actuator 162 b, and a fourth secondaryactuator 162 c), with each blocker door and each secondary actuatorhaving the elements and functionalities as described herein with respectto blocker door 136 and secondary actuator 162.

In various embodiments, blocker door 136 may be coupled at a hinge 164to translating sleeve 125 and at a hinge 166 to secondary actuator 162.Secondary actuator 162 may be coupled to translating sleeve 125 at anysuitable location, such as at a hinge 168. Each of hinge 164, hinge 166,and hinge 168 is configured to enable blocker door 136 to pivot relativeto translating sleeve 125 and in radially inward direction toward innerfixed structure 110, with momentary reference to FIGS. 1B and 1C, inrespond to translation of translating sleeve 125 aft. In variousembodiments, primary actuator 160 is coupled to first translating sleeveat a joint 170 and to fixed structure 152 at a joint 172.

With continued reference to FIGS. 2A and 2B, thrust reverser 102includes a drive system 180 configured to drive or otherwise operateblocker doors 136. In various embodiments, drive system 180 includesprimary actuator 160, secondary actuator(s) 162, and a torque shaft 182.Torque shaft 182 is configured to operationally couple primary actuator160 to secondary actuator(s) 162. In various embodiments, torque shaft182 may be a single, unibody member rotationally coupled to primaryactuator 160 and each secondary actuator 162, or in various embodiments,torque shaft 182 may include a plurality of discrete links rotationallycoupled between primary actuator 160 and secondary actuators 162.

In various embodiments, primary actuator 160 includes a primary rod 184and a primary (or master) gear 186 rotationally coupled to primary rod184. Primary rod 184 may be attached to fixed structure 152 at joint172. Primary rod 184 may include a plurality of teeth 188 configured toengage (e.g., intermeshed with) primary gear 186. In this regard,primary gear 186 is configured to rotate in response to lineartranslation of primary rod 184 (e.g., fore and aft translation). Inaccordance with various embodiments, torque shaft 182 is rotationallycoupled (e.g., via splined connection or any other suitable connectionmeans) to primary gear 186. In this regard, rotation of primary gear 186drives rotation of torque shaft 182.

In accordance with various embodiments, secondary actuator 162 includesa secondary (or slave) gear system 190 and a link 192. Secondary gearsystem 190 is rotationally coupled to torque shaft 182, such thatrotation of torque shaft 182 drives rotation of secondary gear system190. Rotation of secondary gear system 190 is configured to drive atranslation of link 192. Secondary gear system 190 may include a geartrain, a power hinge, a crank, and/or any desired connector capable oftranslating link 192 in response to rotation of torque shaft 182. Link192 is attached to blocker door 136 at, for example, hinge 166.

Referring to FIG. 2A, thrust reverser 102 is illustrated in a stowedconfiguration. In the stowed configuration, blocker door 136 assumes astowed-blocker-door position, such that blocker door 136 does notgenerally interfere with a bypass flow. Referring to FIG. 2B, thrustreverser 102 is illustrated in a deployed configuration. In the deployedconfiguration, blocker door 136 assumes a deployed-blocker-doorposition, such that blocker door 136 extends into and interferes with(e.g., blocks) a bypass flow. In the deployed configuration, a distance194 between translating sleeve 125 and fixed structure 152 is increased,as compared to distance 194, when translating sleeve 125 is in thestowed configuration of FIG. 2A.

During operation, for example, during a transition of thrust reverser102 from the stowed configuration to the deployed configuration, sleeveactuator 132 drives first translating sleeve section 124 away from fixedstructure 152 (e.g., aft). Driving translating sleeve 125 from thestowed configuration (as illustrated in FIG. 2A) to the deployedconfiguration (as illustrated in FIG. 2B) causes teeth 188 of primaryrod 184 to engage and rotate primary gear 186 in a first circumferentialprimary gear direction (e.g., counterclockwise). In this regard,translating sleeve 125 and primary gear 186, which is affixed totranslating sleeve 125 translate relative to primary rod 184, which isaffixed to fixed structure 152, in a first linear direction in responseto translation of thrust reverser 102 to the deployed configuration.Translation of translating sleeve 125 in the first linear directiondrives rotation of primary gear 186 in the first circumferential primarygear direction. The rotation of primary gear 186 in the firstcircumferential primary gear direction drives rotation of torque shaft182 in a first circumferential torque shaft direction (e.g.,counterclockwise). Rotation of torque shaft 182 in the firstcircumferential torque shaft direction, in turn, drives rotation ofsecondary gear system 190 of secondary actuator 162 in a first gearsystem direction. Rotation of secondary gear system 190 in the firstgear system direction drives translation of link 192 in a first linkdirection, thereby forcing blocker door 136 into thedeployed-blocker-door position.

During a transition of thrust reverser 102 from the deployedconfiguration to the stowed configuration, sleeve actuator 132translates translating sleeve 125 toward fixed structure 152. Drivingtranslating sleeve 125 from the deployed configuration (as illustratedin FIG. 2B) to the stowed configuration (as illustrated in FIG. 2A)causes teeth 188 of primary rod 184 to engage and rotate primary gear186 in a second circumferential primary gear direction (e.g., clockwise)opposite the first circumferential primary gear direction. In thisregard, translating sleeve 125 and primary gear 186, which is affixed totranslating sleeve 125, translate relative to primary rod 184 in asecond linear direction opposite the first linear direction, duringtranslation of thrust reverser 102 to the stowed configuration. Thetranslation of translating sleeve 125 in the second linear direction(e.g., forward) drives rotation of primary gear 186 in the secondcircumferential primary gear direction. The rotation of primary gear 186in the second circumferential primary gear direction drives rotation oftorque shaft 182 in a second circumferential torque shaft direction(e.g., clockwise) opposite the first circumferential torque shaftdirection. Rotation of torque shaft 182 in the second torque shaftdirection, in turn, drives rotation of secondary gear system 190 ofsecondary actuator 162 in a second gear system direction opposite thefirst gear system direction. Rotation of secondary gear system 190 inthe second gear system direction drives translation of link 192 in asecond link direction opposite the first link direction, thereby forcingblocker door 136 into the stowed-blocker-door position.

In various embodiments, blocker door 136 may be biased, for example, apre-load may be applied to blocker door 136 and/or to link 192, in orderto force blocker door 136 to remain in the stowed-blocker-door position(i.e., raised) during flight, thereby tending to prevent blocker door136 from deploying (i.e., lowering) inadvertently and creating dragwithin the bypass air flow duct.

Referring now to FIGS. 3A, 3B and 3C, schematic views of a drive system210 configured to drive translation of translating nozzle 128. Inaccordance with various embodiments, thrust reverser 102 is configuredto translate between the stowed configuration and the deployedconfiguration via, for example, drive system 180 as described above withreference to FIGS. 2A and 2B, and variable area fan nozzle 104 is alsoconfigured to translate between a closed position and an open positionvia drive system 210. As described above with reference to FIGS. 1A, 1B,and 1C, translating nozzle 128 is configured for selective translation(e.g., moved fore and aft) to vary exit area “A_(EXIT)” of the exit ofvariable area fan nozzle 104 and to adjust an amount of the bypass flowspilled through upstream exit 140.

In various embodiments, drive system 210 includes a primary (or master)actuator 220, one or more secondary (or slave) actuators 222, and atorque shaft 224 operationally coupling primary actuator 220 andsecondary actuator(s) 222. Drive system 210 is configured to translatefirst nozzle section 127 of translating nozzle 128 in the fore and aftdirections (as indicated by bidirectional arrow 131). While FIGS. 3A, 3Band 3C illustrate first nozzle section 127, it should be understood thattranslating nozzle 128 may include multiple nozzle portions, such as,for example, second nozzle section 129 in FIG. 1A, and that translationof each nozzle portion may be controlled by a nozzle drive system havingthe elements and functionalities as described herein with reference tonozzle drive system 210.

Primary actuator 220 may be coupled between fixed structure 152 andfirst translating sleeve section 124 of thrust reverser 102. In variousembodiments, primary actuator 220 may include a closing actuator 230, anopening primary actuator 232, a first primary rod 234, a second primaryrod, 236, and a primary gear 238. Closing actuator 230 and openingactuator 232 are attached to fixed structure 152. For example, invarious embodiments, closing actuator 230 includes a cylinder 240mounted to fixed structure 152, and opening actuator 232 includes acylinder 242 mounted to fixed structure 152. Closing actuator 230further includes a piston 244, which translates linearly (e.g.,telescopes) relative to cylinder 240. Opening actuator 232 furtherincludes a piston 246, which translates linearly (e.g., telescopes)relative to cylinder 242. Closing and opening actuators 230, 232 may behydraulic, pneumatic, electromechanical, or any other desired type ofactuator.

Closing actuator 230 drives translation of first primary rod 234 in afirst linear direction 250. Opening actuator 232 drives translation ofsecond primary rod 236 in first linear direction 250 (e.g., aft). Firstand second primary rods 234, 236 may be located, at least partially,within a housing (or other structure) 260 attached to first translatingsleeve section 124. Housing 260 is configured to support, oraccommodate, linear translation of first and second primary rods 234,236 as driven by pistons 244, 246, respectively.

In accordance with various embodiments, primary gear 238 is rotationallycoupled to first primary rod 234 and second primary rod 236. In variousembodiments, first primary rod 234 may include a plurality of teeth 262configured to engage (e.g., intermeshed with) primary gear 238, andsecond primary rod 236 may include a plurality of teeth 264 configuredto engage (e.g., intermeshed with) primary gear 238. In this regard,primary gear 238 is configured to rotate in response to lineartranslation (e.g., fore and aft translation) of first primary rod 234and/or of second primary rod 236. In accordance with variousembodiments, torque shaft 224 is rotationally coupled (e.g. via splinedconnection or any other suitable connection means) to primary gear 238.In this regard, rotation of primary gear 238 drives rotation of torqueshaft 224.

In various embodiments, torque shaft 224 may be a single, unibody memberrotationally coupled to primary gear 238 and each secondary actuator 222or in various embodiments, torque shaft 224 may include a plurality ofdiscrete links rotationally coupled between primary gear 238 andsecondary actuators 222.

Secondary actuators 222 may be coupled between translating nozzle 128and translating sleeve 125 (e.g., between first nozzle section 127 oftranslating nozzle 128 and first translating sleeve section 124 oftranslating sleeve 125). In accordance with various embodiments,secondary actuators 222 each includes a secondary (or slave) gear 270and a secondary rod 272. Secondary gear 270 is rotationally coupled totorque shaft 224 (e.g., splined connection or any other suitableconnection means), such that rotation of torque shaft 224 drivesrotation of secondary gear 270. Secondary gear 270 is also rotationallycoupled to secondary rod 272. In various embodiments, secondary rod 272may include a plurality of teeth 274 configured to engage (e.g.,intermeshed with) secondary gear 270. In this regard, rotation ofsecondary gear 270, as driven by rotation of torque shaft 224, driveslinear translation (e.g., fore and aft translation) of secondary rod272. Secondary rod 272 is attached to first nozzle section 127 at ajoint 276. In various embodiments, secondary rod 272 may be located, atleast partially, within a housing (or other structure) 278 attached tofirst translating sleeve section 124. Housing 278 is configured tosupport and/or accommodate, linear translation of secondary rod 272 asdriven by secondary gear 270, which may also be located in housing 278.

Referring to FIG. 3A, variable area fan nozzle 104 is illustrated in aclosed or nearly closed position. In the closed position, translatingnozzle 128 is located proximate an aft end of first translating sleevesection 124 such that upstream exit 140 is completely closed orotherwise open only a nominal amount. In the closed position, piston 244of closing actuator 230 is positioned substantially toward, and/orcloser to, housing 260 and primary gear 238, as compared to piston 246of opening actuator 232, which is positioned away from housing 260 andprimary gear 238. In this regard, in the closed position, first primaryrod 234 may be located closer to translating nozzle 128 as compared tosecond primary rod 236.

Referring to FIG. 3B, variable area fan nozzle 104 is illustrated in anopen position. In the open position, translating nozzle 128 is locateddistal (i.e., a greater distance from) the aft end of first translatingsleeve section 124 such that upstream exit 140 is open an amount greaterthan the completely closed or nominally open positions, thereby allowinga greater portion of the bypass flow to flow through upstream exit 140.In the open position, piston 244 of closing actuator 230 is positionedsubstantially away, and/or farther, from housing 260 and primary gear238, as compared to piston 246 of opening actuator 232, which ispositioned substantially toward housing 260 and primary gear 238. Inthis regard, in the open position, first primary rod 234 may be locatedfarther from translating nozzle 128 as compared to second primary rod236.

During operation, for example, in response to translation of variablearea fan nozzle 104 from the closed position to the open position,opening actuator 232 drives piston 246 out of cylinder 242 and towardssecond primary rod 236 and primary gear 238, thereby causing secondprimary rod 236 to translate in first linear direction 250 (e.g., aft).Translation of second primary rod 236 in first linear direction 250drives rotation of primary gear 238 in a first circumferential primarygear direction (e.g., counterclockwise). Rotation of primary gear 238 inthe first circumferential primary gear direction drives first primaryrod 234 in a second linear direction 252 (e.g., forward) opposite firstlinear direction 250. Translation of first primary rod 234 in secondlinear direction 252 may drive piston 244 in second linear direction 252and into cylinder 240.

Rotation of primary gear 238 in the first circumferential primary geardirection drives rotation of torque shaft 224 in a first circumferentialtorque shaft direction (e.g., counterclockwise). Rotation of torqueshaft 224 in the first circumferential torque shaft direction drivesrotation of secondary gear 270 in a first circumferential secondary geardirection (e.g., counterclockwise). Rotation of secondary gear 270 inthe first circumferential secondary gear direction drives lineartranslation of secondary rod 272 in first linear direction 250, therebyforcing translating nozzle 128 away from translating sleeve 125 (i.e.,in first linear direction 250) and increasing an axial length ofupstream exit 140.

In response to translation of variable area fan nozzle 104 from the openposition to the closed position, closing actuator 230 drives piston 244out of cylinder 240 and towards first primary rod 234 and primary gear238, thereby causing first primary rod 234 to translate in first lineardirection 250 (e.g., aft). Translation of first primary rod 234 in firstlinear direction 250 drives rotation of primary gear 238 in a secondcircumferential primary gear direction (e.g., clockwise) opposite thefirst circumferential primary gear direction. Rotation of primary gear238 in the second circumferential primary gear direction drives secondprimary rod 236 in second linear direction 252 (e.g., forward).Translation of second primary rod 236 in second linear direction 252 maydrive piston 246 in second linear direction 252 and into cylinder 242.

Rotation of primary gear 238 in the second circumferential primary geardirection drives rotation of torque shaft 224 in a secondcircumferential torque shaft direction (e.g., clockwise) opposite thefirst circumferential torque shaft direction. Rotation of torque shaft224 in the second circumferential torque shaft direction drives rotationof secondary gear 270 in a second circumferential secondary geardirection (e.g., clockwise). Rotation of secondary gear 270 in thesecond circumferential secondary gear direction drives lineartranslation of secondary rod 272 in second linear direction 252, therebyforcing translating nozzle 128 towards translating sleeve 125 (i.e., insecond linear direction 252) and decreasing the axial length of upstreamexit 140.

Still referring to FIGS. 3A, 3B and 3C, drive system 210 includes alocking assembly 280 configured to block, reduce, or otherwise preventrelative translation between translating sleeve 125 and translatingnozzle 128 in response to translation of thrust reverser 102 from thestowed configuration to the deployed configuration (e.g., in response toan increase in distance 194). In various embodiments, for example,locking assembly 280 may include an interference member 282 and acoupling member (e.g., a strut) 284. Interference member 282 may bebiased toward primary gear 238. Coupling member 284 may be coupled tointerference member 282. Coupling member 284 is configured to maintainlocking assembly 280 in an unlocked state, when thrust reverser 102 isin the stowed position, and to cause locking assembly 280 to translateto a locked state, in response to thrust reverser 102 translating to thedeployed position.

In the unlocked state (FIGS. 3A and 3B), translating nozzle 128 isallowed to translate fore and aft. In the locked state (FIG. 3C),translating nozzle 128 is locked to translating sleeve 125 and thustravels with translating sleeve 125 as thrust reverser 102 is deployed.In the unlocked state and/or when thrust reverser 102 is in the stowedposition, coupling member 284 may contact fixed structure 152. Couplingmember 284 being in contact with fixed structure 152 may locateinterference member 282 a predetermined distance D away from primarygear 238. In this regard, primary gear 238 may be able to rotate in thefirst and second circumferential primary gear directions when couplingmember is contacting fixed structure 152 (i.e., when locking assembly280 is in the unlocked state). In the locked state and/or in response totranslation of thrust reverser 102, from the stowed configuration to thedeployed configuration, coupling member 284 separates from (i.e., doesnot contact) fixed structure 152. In response to coupling member 284being separated from fixed structure 152, the biasing force applied tointerference member 282 forces interference member 282 into contact withprimary gear 238, thereby generating an interference with primary gear238 that prevents or reduces rotation of primary gear 238. Blockingrotation of primary gear 238 prevents or reduces linear translation oftranslating nozzle 128 with respect to translating sleeve 125. In thisregard, as distance 194 increases, that axial length of upstream exit140 (i.e., the distance between translating nozzle 128 and translatingsleeve 125) tends to remain constant. While the disclosure generallyfocuses on interference member 282 being configured to contact and/orblock rotation of primary gear 238, it is further contemplated andunderstood that locking assembly 280 may also or instead be configuredto block rotation of torque shaft 224 and/or to block rotation ofsecondary gear 270.

Referring now to FIGS. 4A and 4B, schematic views of a thrust reverser302 configured to translate between a stowed configuration and adeployed configuration, respectively, are provided. In variousembodiments, nacelle 108 in FIGS. 1A, 1B, and 1C may include thrustreverser 302 in place of thrust reverser 102. Thrust reverser 302includes a translating sleeve 325 configured to translate in fore andaft directions (as indicated by the bidirectional arrow 330) and isoperated by a sleeve actuator 332, which may comprise any suitableactuation system capable of driving a rapid translation of translatingsleeve 325 for deployment of thrust reverser 302, such as, for example,a ball screw mechanism or a hydraulic cylinder. In various embodiments,sleeve actuator 332 is connected between a fixed structure 326, such as,for example, a torque box, and translating sleeve 325. In variousembodiments, thrust reverser 302 includes a blocker door 336, similar tothe blocker door 136 described above with reference to FIGS. 1B and 1C.As also described above, blocker door 336 is configured to block aportion of a bypass flow when thrust reverser 302 is in a deployedconfiguration. A primary (or master) actuator 360 is connected betweenfixed structure 326 and translating sleeve 325. A secondary (or slave)actuator 362 is connected between translating sleeve 325 and blockerdoor 336. While, for clarity, the disclosure generally focuses onoperation of blocker door 336 and secondary actuator 362, it shall beappreciated, as illustrated in FIGS. 4A and 4B, that thrust reverser 302may include a plurality of blocker doors (e.g., a first blocker door336, a second blocker door 336 a, a third blocker door 336 b, and afourth blocker door 336 c) operated by a plurality of secondaryactuators (e.g., a first secondary actuator 362, a second secondaryactuator 362 a, a third secondary actuator 362 b, and a fourth secondaryactuator 362 c).

In various embodiments, blocker door 336 may be coupled at a hinge 364to the translating sleeve 225 and at a hinge 366 to secondary actuator362. Secondary actuator 362 may be coupled to translating sleeve 325 atany suitable location, such as at a joint 368. Hinge 364, hinge 366,and/or joint 368 are configured to enable blocker door 336 to pivotrelative to translating sleeve 325 and in radially inward directiontoward an inner fixed structure, such as, for example, inner fixedstructure 110 described above with reference to FIGS. 1B and 1C, astranslating sleeve 325 translates aft (i.e., away from fixed structure326). In various embodiments, primary actuator 360 is coupled totranslating sleeve 325 at a joint 370 and to fixed structure 326 at ajoint 372.

With continued reference to FIGS. 4A and 4B, thrust reverser 302includes a drive system 380 configured to control translation of blockerdoor 336. Drive system 380 includes primary actuator 360, secondaryactuator(s) 362, and a torque shaft 382 operationally coupling primaryactuator 360 and secondary actuator(s) 362. In various embodiments,torque shaft 382 may be a single, unibody member rotationally coupled toprimary actuator 360 and each secondary actuator 362, or in variousembodiments, torque shaft 382 may include a plurality of discrete linksrotationally coupled between primary actuator 360 and secondaryactuators 362.

In various embodiments, primary actuator 360 includes a primary rod 384and a primary (or master) gear 386 rotationally coupled to primary rod384. Primary rod 384 may be attached to fixed structure 326 at joint372. Primary rod 384 may include a plurality of teeth 388 configured toengage (e.g., intermeshed with) primary gear 386. In this regard,primary gear 386 is configured to rotate in response to lineartranslation of primary rod 384 (e.g., fore and aft translation). Inaccordance with various embodiments, torque shaft 382 is rotationallycoupled (e.g. via splined connection or any other suitable connectionmeans) to primary gear 386. In this regard, rotation of primary gear 386drives rotation of torque shaft 382.

In accordance with various embodiments, secondary actuator 362 includesa secondary (or slave) gear 390 and a link 392. Secondary gear 390 isrotationally coupled to torque shaft 382, such that rotation of torqueshaft 382 drives rotation of secondary gear 390. Rotation of secondarygear 390 is configured to drive a linear translation of secondary rod392. Secondary rod 392 may include a plurality of teeth 394 configuredto engage (e.g., intermeshed with) secondary gear 390. In this regard,rotation of secondary gear 390 causes secondary rod 392 to translatetoward and away from blocker door 336. Secondary rod 392 is attached toblocker door 336 at, for example, hinge 366.

Referring to FIG. 4A, thrust reverser 302 is illustrated in a stowedconfiguration. In the stowed configuration, blocker door 336 is in astowed-blocker-door position, such that blocker door 336 does notgenerally interfere with a bypass flow. Referring to FIG. 4B, thrustreverser 302 is illustrated in a deployed configuration. In the deployedconfiguration, blocker door 336 is in a deployed-blocker-door position,wherein blocker door 336 extends into and interferes with (e.g., blocks)a bypass flow. In the deployed configuration, a distance 396, betweentranslating sleeve 325 and fixed structure 326 is increased as comparedto distance 396 when translating sleeve 325 is in the stowed configuredillustrated in FIG. 4A.

During operation, thrust reverser 302 may translate from the stowedconfiguration to the deployed configuration, with sleeve actuator 332driving translating sleeve 325 away from fixed structure 326 (e.g.,aft). Translation of translating sleeve 325 from the stowedconfiguration (as illustrated in FIG. 4A) to the deployed configuration(as illustrated in FIG. 4B) causes teeth 388 of primary rod 384 toengage and rotate primary gear 386 in a first primary circumferentialdirection (e.g., counterclockwise). In this regard, translating sleeve325 and primary gear 386, which is affixed to translating sleeve 325,translate relative to primary rod 384, which is coupled to fixedstructure 326, in a first linear direction 350. Translation oftranslating sleeve 325 in first linear direction 350 drives rotation ofprimary gear 386 in the first circumferential primary gear direction.The rotation of primary gear 386 in the first circumferential primarygear direction drives rotation of torque shaft 382 in a firstcircumferential torque shaft direction (e.g., counterclockwise).Rotation of torque shaft 382 in the first circumferential torque shaftdirection, in turn, drives rotation of secondary gear 390 of secondaryactuator 362 in a first circumferential secondary gear direction (e.g.,counterclockwise). Rotation of secondary gear 390 in the firstcircumferential secondary gear direction drives translation of secondaryrod in a first rod direction, thereby forcing blocker door 336 into thedeployed-blocker-door position.

During a transition of thrust reverser 302 from the deployedconfiguration to the stowed configuration, sleeve actuator 332translates translating sleeve 325 towards fixed structure 326 (e.g.,forward). Driving translating sleeve 325 from the deployed configuration(as illustrated in FIG. 4B) to the stowed configuration (as illustratedin FIG. 4A) causes teeth 388 of primary rod 384 to engage and rotateprimary gear 386 in a second circumferential primary gear direction(e.g., clockwise) opposite the first circumferential primary geardirection. In this regard, translating sleeve 325 and primary gear 386,which is attached to translating sleeve 325 translate relative toprimary rod 384, which is attached to fixed structure 326, in a secondlinear direction 352 (e.g., forward) opposite the first linear direction350, in response to translation of thrust reverser 302 to the stowedconfiguration. Translation of translating sleeve 325 in second lineardirection 352 drives rotation of primary gear 386 in the secondcircumferential primary gear direction, which in turn drives rotation oftorque shaft 382 in a second circumferential torque shaft direction(e.g., clockwise) opposite the first circumferential torque shaftdirection. Rotation of torque shaft 382 in the second torque shaftdirection, in turn, drives rotation of secondary gear 390 of secondaryactuator 362 in a second circumferential secondary gear direction (e.g.,clockwise) opposite the first circumferential secondary gear direction.Rotation of secondary gear 390 in the second circumferential secondarygear direction drives translation of secondary rod 392 in a second roddirection opposite the first link direction, thereby forcing blockerdoor 336 into the stowed-blocker-door position.

In various embodiments, blocker door 336 may be biased, for example, apre-load may be applied to blocker door 336 and/or to secondary rod 392and/or secondary gear 390, to force blocker door 336 to remain in thestowed-blocker-door position (i.e., raised) during flight, therebytending to prevent blocker door 336 from deploying (i.e., lowering)inadvertently and creating drag within the bypass air flow duct.

While drive system 180 in FIG. 2, drive system 210 in FIG. 3A, and drivesystem 380 in FIG. 4A are illustrated as having one primary actuator, itis further contemplated and understood that the drive systems mayinclude multiple primary actuators. For example, and with reference toFIG. 5, a schematic view of a drive system 480 including first masteractuator 420 and second master actuator 422 is illustrated. Drive system480 may be operationally coupled to a thrust reverser 402, similar tothrust reverser 102 in FIG. 1A. Thrust reverser 402 is configured totranslate between a stowed configuration and a deployed configuration isprovided. In various embodiments, nacelle 108 in FIGS. 1A, 1B, and 1Cmay include thrust reverser 402 in place of thrust reverser 102. Thrustreverser 402 includes a translating sleeve 425 configured to translatein fore and aft directions (as indicated by the bidirectional arrow430). Translating sleeve 425 may be operated by a sleeve actuator 432,which may comprise any suitable actuation system capable of driving arapid translation of translating sleeve 425 for deployment of thrustreverser 402.

In various embodiments, sleeve actuator 432 is connected between a fixedstructure 426, such as, for example, a torque box, and translatingsleeve 425. In various embodiments, thrust reverser 402 includes ablocker door 436, similar to the blocker door 136 described above withreference to FIGS. 1B and 1C. As also described above, blocker door 436is configured to block a portion of a bypass flow when thrust reverser402 is in a deployed configuration.

First primary (or master) actuator 420 and second primary actuator areconnected between fixed structure 426 and translating sleeve 425. Asecondary (or slave) actuator 462 is connected between translatingsleeve 425 and blocker door 436. While, for clarity, the disclosuregenerally focuses on operation of blocker door 436 and secondaryactuator 462, it shall be appreciated, as illustrated in FIG. 5, thatthrust reverser 402 may include a plurality of blocker doors (e.g., afirst blocker door 436, a second blocker door 436 a, a third blockerdoor 436 b, and a fourth blocker door 436 c) operated by a plurality ofsecondary actuators (e.g., a first secondary actuator 462, a secondsecondary actuator 462 a, a third secondary actuator 462 b, and a fourthsecondary actuator 462 c).

With continued reference to FIG. 5, thrust reverser 402 includes drivesystem 480 configured to control translation of blocker door 436. Drivesystem 480 includes first and second primary actuators 420, 422,secondary actuator(s) 462, and a torque shaft 482 operationally couplingfirst primary actuator 420 and secondary actuator(s) 462 and secondprimary actuator 422 and secondary actuator(s) 462. In variousembodiments, torque shaft 482 may be a single, unibody memberrotationally coupled to first and second primary actuators 420, 422 andeach secondary actuator 462, or in various embodiments, torque shaft 482may include a plurality of discrete links rotationally coupled betweenfirst primary actuator 420, secondary actuators 462, and second primaryactuator 422.

In various embodiments, first primary actuator 420 includes a firstprimary rod 484 and a first primary (or master) gear 486 rotationallycoupled to first primary rod 484. In various embodiments, second primaryactuator 422 includes a second primary rod 444 and a second primary (ormaster) gear 446 rotationally coupled to second primary rod 444 Firstand second primary rods 484, 444 may be attached to fixed structure 426and are configured to engage (e.g., are intermeshed with) first andsecond primary gears 486, 446, respectively. In this regard, first andsecond primary gears 486, 446 are configured to rotate in response tolinear translation (e.g., fore and aft translation) of translatingsleeve 425 relative to first and second primary rods 484, 444. Inaccordance with various embodiments, torque shaft 482 is rotationallycoupled (e.g. via splined connection or any other suitable connectionmeans) to first and second primary gears 486, 446. In this regard,rotation of first and second primary gears, 486, 446 drive rotation oftorque shaft 482, which in turn drives rotation of the secondary (slave)gears 490 of secondary actuators 462. Rotation of secondary gears 490drives translation of links 492, thereby translating blocker doors 436between the stowed-blocker-door and deployed-blocker-door position.

Benefits, other advantages, and solutions to problems have beendescribed herein with regard to specific embodiments. Furthermore, theconnecting lines shown in the various figures contained herein areintended to represent exemplary functional relationships and/or physicalcouplings between the various elements. It should be noted that manyalternative or additional functional relationships or physicalconnections may be present in a practical system. However, the benefits,advantages, solutions to problems, and any elements that may cause anybenefit, advantage, or solution to occur or become more pronounced arenot to be construed as critical, required, or essential features orelements of the disclosure. The scope of the disclosure is accordinglyto be limited by nothing other than the appended claims, in whichreference to an element in the singular is not intended to mean “one andonly one” unless explicitly so stated, but rather “one or more.”Moreover, where a phrase similar to “at least one of A, B, or C” is usedin the claims, it is intended that the phrase be interpreted to meanthat A alone may be present in an embodiment, B alone may be present inan embodiment, C alone may be present in an embodiment, or that anycombination of the elements A, B and C may be present in a singleembodiment; for example, A and B, A and C, B and C, or A and B and C.Different cross-hatching is used throughout the figures to denotedifferent parts but not necessarily to denote the same or differentmaterials.

Systems, methods and apparatus are provided herein. In the detaileddescription herein, references to “one embodiment,” “an embodiment,”“various embodiments,” etc., indicate that the embodiment described mayinclude a particular feature, structure, or characteristic, but everyembodiment may not necessarily include the particular feature,structure, or characteristic. Moreover, such phrases are not necessarilyreferring to the same embodiment. Further, when a particular feature,structure, or characteristic is described in connection with anembodiment, it is submitted that it is within the knowledge of oneskilled in the art to affect such feature, structure, or characteristicin connection with other embodiments whether or not explicitlydescribed. After reading the description, it will be apparent to oneskilled in the relevant art(s) how to implement the disclosure inalternative embodiments.

Furthermore, no element, component, or method step in the presentdisclosure is intended to be dedicated to the public regardless ofwhether the element, component, or method step is explicitly recited inthe claims. No claim element is intended to invoke 35 U.S.C. 112(f)unless the element is expressly recited using the phrase “means for.” Asused herein, the terms “comprises,” “comprising,” or any other variationthereof, are intended to cover a non-exclusive inclusion, such that aprocess, method, article, or apparatus that comprises a list of elementsdoes not include only those elements but may include other elements notexpressly listed or inherent to such process, method, article, orapparatus.

Finally, any of the above described concepts can be used alone or incombination with any or all of the other above described concepts.Although various embodiments have been disclosed and described, one ofordinary skill in this art would recognize that certain modificationswould come within the scope of this disclosure. Accordingly, thedescription is not intended to be exhaustive or to limit the principlesdescribed or illustrated herein to any precise form. Many modificationsand variations are possible in light of the above teaching.

What is claimed is:
 1. A nacelle, comprising: a fixed structure; athrust reverser including a translating sleeve and a blocker door,wherein the translating sleeve is configured to translate relative tothe fixed structure; a variable area fan nozzle aft of the thrustreverser and including a translating nozzle a first drive systemoperationally coupled to the thrust reverser, the first drive systemcomprising: a first primary actuator coupled to the fixed structure andincluding a first primary rod and a first primary gear rotationallycoupled to the first primary rod; a first torque shaft rotationallycoupled to the first primary gear; and a first secondary actuatoroperationally coupled to the first primary actuator via the first torqueshaft, wherein the first secondary actuator is configured to rotate theblocker door of the thrust reverser between a stowed-blocker-doorposition and a deployed-blocker-door position in response to rotation ofthe first primary gear; and a second drive system operationally coupledto the translating nozzle, the second drive system comprising: a secondprimary actuator coupled to the fixed structure and including a secondprimary rod and a second primary gear rotationally coupled to the secondprimary rod; a second torque shaft rotationally coupled to the secondprimary gear; a second secondary actuator operationally coupled to thesecond primary actuator via the second torque shaft, the secondsecondary actuator comprising a secondary gear rotationally coupled tothe second torque shaft and a first secondary rod coupled to thetranslating nozzle and configured to be driven linearly by rotation ofthe secondary gear; and a locking assembly configured to restricttranslation of the translating nozzle relative to the translating sleevein response to translation of the translating sleeve away from the fixedstructure, wherein the locking assembly comprises an interference memberbiased toward the second primary gear of the second drive system, and acontact member coupled to the interference member and configured tocontact the fixed structure when the thrust reverser is in a stowedconfiguration.
 2. The nacelle of claim 1, further comprising a sleeveactuator configured to translate the translating sleeve in a foredirection and an aft direction relative to the fixed structure.
 3. Thenacelle of claim 1, wherein a housing of the second primary actuator iscoupled to the translating sleeve of the thrust reverser.
 4. The nacelleof claim 1, wherein the second primary actuator comprises: an openingactuator, wherein translation of the second primary rod is driven by theopening actuator; a closing actuator; and a third primary rod, whereintranslation of the third primary rod is driven by the closing actuator,and wherein the second primary gear is rotationally coupled to thesecond primary rod and the third primary rod.
 5. The nacelle of claim 4,wherein the second primary rod includes a plurality of first teethconfigured to engage the second primary gear, and wherein the thirdprimary rod includes a plurality of second teeth configured to engagethe second primary gear.
 6. The nacelle of claim 1, wherein the firstsecondary rod includes a plurality of teeth configured to engage thesecondary gear.
 7. The nacelle of claim 1, wherein the first primarygear is configured to translate linearly relative to the first primaryrod in response to translation of the translating sleeve.
 8. The nacelleof claim 7, wherein the first secondary actuator is configured to rotatethe blocker door to the deployed-blocker-door position in response torotation of the first primary gear in a first circumferential primarygear direction, and wherein the first secondary actuator is configuredto rotate the blocker door to the stowed-blocker-door position inresponse to rotation of the first primary gear in a secondcircumferential primary gear direction opposite the firstcircumferential primary gear direction.
 9. The nacelle of claim 8,wherein the first secondary actuator comprises: a slave gear systemrotationally coupled to the first torque shaft; and a link coupled tothe slave gear system, wherein the link is configured to rotate theblocker door in response to rotation of the slave gear system.
 10. Thenacelle of claim 8, wherein the first secondary actuator comprises: aslave gear rotationally coupled to the first torque shaft; and a secondsecondary rod including a plurality of teeth configured to engage theslave gear, wherein the second secondary rod is configured to rotate theblocker door in response to rotation of the slave gear.
 11. A nacelle,comprising: a fixed structure; a thrust reverser including a translatingsleeve, wherein the translating sleeve is configured to translaterelative to the fixed structure; a variable area fan nozzle aft of thethrust reverser and including a translating nozzle; and a drive systemoperationally coupled to the translating nozzle, the drive systemcomprising: a primary actuator coupled to the fixed structure andincluding a first primary rod and a primary gear rotationally coupled tothe first primary rod; a torque shaft rotationally coupled to theprimary gear; a secondary actuator operationally coupled to the primaryactuator via the torque shaft, the secondary actuator comprising asecondary gear rotationally coupled to the torque shaft and a secondaryrod coupled to the translating nozzle and configured to be drivenlinearly by rotation of the secondary gear; and a locking assemblyconfigured to restrict translation of the translating nozzle relative tothe translating sleeve in response to translation of the translatingsleeve away from the fixed structure, wherein the locking assemblycomprises an interference member biased toward the primary gear of thedrive system, and a contact member coupled to the interference memberand configured to contact the fixed structure when the thrust reverseris in a stowed configuration.
 12. The nacelle of claim 11, furthercomprising a sleeve actuator configured to translate the translatingsleeve in a fore direction and an aft direction relative to the fixedstructure.
 13. The nacelle of claim 11, wherein a housing of the primaryactuator is coupled to the translating sleeve of the thrust reverser.14. The nacelle of claim 11, wherein the primary actuator comprises: anopening actuator, wherein translation of the first primary rod is drivenby the opening actuator; a closing actuator; and a second primary rod,wherein translation of the second primary rod is driven by the closingactuator, and wherein the primary gear is rotationally coupled to thefirst primary rod and the second primary rod.
 15. A nacelle, comprising:a fixed structure; a thrust reverser including a translating sleeve,wherein the translating sleeve is configured to translate relative tothe fixed structure; a variable area fan nozzle aft of the thrustreverser and including a translating nozzle; and a drive systemoperationally coupled to the translating nozzle, the drive systemcomprising: a primary actuator coupled to the fixed structure andincluding a first primary rod and a primary gear rotationally coupled tothe first primary rod; a torque shaft rotationally coupled to theprimary gear; a secondary actuator coupled to the translating nozzle andthe torque shaft; and a locking assembly configured to restricttranslation of the translating nozzle relative to the translating sleevein response to translation of the translating sleeve away from the fixedstructure, wherein the locking assembly comprises an interference memberbiased toward the primary gear of the drive system, and a contact membercoupled to the interference member and configured to contact the fixedstructure when the thrust reverser is in a stowed configuration.
 16. Thenacelle of claim 15, wherein a housing of the primary actuator iscoupled to the translating sleeve of the thrust reverser.
 17. Thenacelle of claim 15, wherein the primary actuator comprises: an openingactuator, wherein translation of the first primary rod is driven by theopening actuator; a closing actuator; and a second primary rod, whereintranslation of the second primary rod is driven by the closing actuator,and wherein the primary gear is rotationally coupled to the firstprimary rod and the second primary rod.